US8061965B2 - Ring structure of metal construction having a run-in lining - Google Patents

Ring structure of metal construction having a run-in lining Download PDF

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Publication number
US8061965B2
US8061965B2 US11/578,862 US57886205A US8061965B2 US 8061965 B2 US8061965 B2 US 8061965B2 US 57886205 A US57886205 A US 57886205A US 8061965 B2 US8061965 B2 US 8061965B2
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United States
Prior art keywords
wall
metal
ring structure
woven fabric
recited
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related, expires
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US11/578,862
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English (en)
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US20090263239A1 (en
Inventor
Manfred A. Daeubler
Ulrike Hain
Werner Humhauser
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Aero Engines GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Assigned to MTU AERO ENGINES GMBH reassignment MTU AERO ENGINES GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HUMHAUSER, WERNER, HAIN, ULRIKE, MENDRITZKI, RENATE, MUELLER-WITTEK, HORST
Publication of US20090263239A1 publication Critical patent/US20090263239A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/236—Diffusion bonding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/238—Soldering
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/601—Fabrics

Definitions

  • the present invention is directed to a ring structure of metal construction for a rotor blade region of axial flow compressor and turbine stages.
  • the wall structure exhibit sufficient dimensional stability and geometric precision. It is critical that the geometry be altered as little as possible by thermal and mechanical influences. The mostly hot working gas should essentially act only on the interior side of the structure; losses due to leakage through the structure must be minimized. In steady-state operation, it is advantageous when the mostly thermally induced dimensional variation of the wall structure is adapted temporally and in terms of magnitude to that of the bladed rotor. Since mechanical contacting between the blade tips and the wall structure is hardly avoidable under certain applications of force, the interior side of the wall structure should be designed to be deformable, resilient and, accordingly, to have run-in capability, at least on the blade-tip side.
  • the annular chamber structure in accordance with German patent DE 100 20 673 C2 has an inner wall, which is interrupted over its circumference by a plurality of axially or primarily axially extending expansion joints.
  • An inner wall segmented in this manner by expansion joints has the disadvantage that flow losses can occur.
  • the complexity of the ring structure and thus the assembly as well as manufacturing outlay are increased by an inner wall segmented in this manner.
  • chipping off, washout or damage due to erosion can occur at the edges of the expansion joints, further increasing the flow losses.
  • an object of the present invention is to devise a novel type of ring structure of metal construction.
  • the present invention provides a ring structure of metal construction for a rotor blade region of axial flow compressor and turbine stages, in particular in gas turbine engines, comprising an annular outer wall ( 11 ), an annular inner wall ( 12 ) that is spaced with very little radial clearance from the blade tips, and a connecting structure ( 13 ) positioned between the outer wall ( 11 ) and the inner wall ( 12 ) and designed as a hollow-chamber structure, the outer wall ( 11 ) being designed as a closed, mechanically stable housing wall of the compressor or turbine stage, and the connecting structure ( 13 ) designed as a hollow-chamber structure being connected to the outer wall ( 11 ) and the inner wall ( 12 ), wherein the inner wall ( 12 ), which is designed as a closed, mechanically stable structure that serves as an run-in lining for the blade tips, is made of a metal woven fabric and/or of a metal felt.
  • the inner wall is designed as a closed, mechanically stable structure that is made of a metal woven fabric and/or of a metal felt and serves as a run-in lining for the blade tips.
  • the metal woven fabric and/or the metal felt is preferably fabricated from a metal alloy that is oxidation-resistant at high temperatures, in particular an iron-, nickel- or cobalt-based alloy.
  • a ring structure of metal construction whose inner wall has a closed design and is made of a metal woven fabric and/or of a metal felt.
  • the closed structure of the inner wall makes it possible to minimize flow losses.
  • the ring structure according to the present invention is simpler in design than the segmented design known from the related art.
  • FIG. 1 shows a ring structure of metal construction according to the present invention in accordance with a first exemplary embodiment of the present invention in a schematic side view;
  • FIG. 2 shows detail II of the ring structure in accordance with FIG. 1 ;
  • FIG. 3 shows a ring structure of metal construction according to the present invention in accordance with a second exemplary embodiment of the present invention in a schematic side view;
  • FIG. 4 illustrates detail IV of the ring structure in accordance with FIG. 3 ;
  • FIG. 5 depicts a ring structure of metal construction according to the present invention in accordance with a third exemplary embodiment of the present invention in a schematic side view
  • FIG. 6 shows detail VI of the ring structure in accordance with FIG. 5 .
  • FIGS. 1 and 2 show a first exemplary embodiment of a ring structure 10 according to the present invention, FIG. 2 illustrating detail II of FIG. 1 on an enlarged scale.
  • Ring structure 10 of the exemplary embodiment of FIGS. 1 and 2 includes a circular outer wall 11 , a circular inner wall 12 , as well as connecting structure 13 positioned in a sandwich-type arrangement between outer wall 11 and inner wall 12 .
  • Outer wall 11 is designed as a closed, mechanically stable housing wall of a compressor stage or turbine stage of a gas turbine, in particular of an aircraft engine.
  • Connecting structure 13 positioned between outer wall 11 and inner wall 12 is designed as a hollow-chamber structure.
  • hollow-chamber structure 13 may have hexagonal, rectangular or also round chambers, in one cross-sectional direction, disposed in parallel to the inner wall or outer wall of ring structure 10 . Chambers that are hexagonal in cross section have a so-called honeycomb structure.
  • inner wall 12 is designed as a closed and mechanically stable structure.
  • Inner wall 12 serves, on the one hand, to mechanically stabilize ring structure 10 and, on the other hand, as a run-in lining for blade tips of rotating blades (not shown).
  • Inner wall 12 which is designed along the lines of the present invention as an intrinsically closed structure, is made of a metal woven fabric and/or metal felt.
  • a metal woven fabric is a structure in which metallic fibers or threads extend in a systematic pattern.
  • a metal felt is a structure in which metallic fibers are oriented in a randomly or stochastically distributed pattern.
  • the term metal woven fabric also refers to a knit mesh of metal fibers.
  • inner wall 12 By using an intrinsically closed structure of metal woven fabric and/or metal felt as inner wall 12 , one avoids gaps or joints within inner wall 12 . This makes it possible to minimize flow losses.
  • the metal woven fabric and/or the metal felt are capable of absorbing thermally produced strains without the danger of crack formation. This eliminates the need for expansion joints within inner wall 12 .
  • inner wall 12 designed as a closed structure has a simple design.
  • connecting structure 13 is permanently joined together.
  • connecting structure 13 is permanently joined at the radially external end to outer wall 11 and, on the other side, at radially interior end to inner wall 12 .
  • connecting structure 13 may be soldered to inner wall 12 as well as to outer wall 11 .
  • it is possible to join connecting structure 13 to inner wall 12 and outer wall 11 for example by so-called surface diffusion welding or by sintering.
  • outer wall 11 , inner wall 12 , as well as connecting structure 13 are permanently joined together to form an overall structure, namely ring structure 10 according to the present invention.
  • inner wall 12 serves, on the one hand, to mechanically stabilize ring structure 10 according to the present invention and, on the other hand, as a run-in lining.
  • inner wall 12 and, accordingly, the metal woven fabric and/or the metal felt of inner wall 12 are made of a material that is oxidation-resistant at high temperatures.
  • the metal woven fabric or the metal felt may, for example, be fabricated from a metal alloy based on a nickel material, iron material or also a cobalt material.
  • FIGS. 1 and 2 show a butt joint 14 of two mutually contiguous edges of the metal woven fabric and/or of the metal felt which is used to produce inner wall 12 .
  • the edges of butt joint 14 extend radially, so that the two edges are, in fact, mutually contiguous in the area of butt joint 14 , but do not overlap.
  • FIG. 3 through 6 show two other exemplary embodiments of ring structures 15 and 16 according to the present invention.
  • the exemplary embodiments of FIG. 3 through 6 differ from the exemplary embodiment of FIGS. 1 and 2 merely in the formation of the butt joint in the region of inner wall 12 .
  • the exemplary embodiments correspond in all other details, so that the same reference numerals are used for equivalent subassemblies to avoid unnecessary repetition.
  • a butt joint 17 which extends obliquely to the radial direction; thus, on the one hand, it extends radially and, on the other hand, in the circumferential direction of ring structure 15 .
  • the corresponding edges overlap without any thickening of material.
  • FIGS. 5 and 6 show an exemplary embodiment of a ring structure 16 according to the present invention which, in the region of inner wall 12 , has a butt joint 18 whose mutually abutting edges overlap one another, forming a region of thickened material 19 .
  • region of thickened material 19 is directed radially outwardly in this context; accordingly, region of thickened material 19 extends into the region of connecting structure 13 .
  • the chambers of connecting structure 13 may be shortened in conformance therewith in the region in which region of thickened material 19 extends.
  • a metallic ring structure is provided, whose inner wall is closed and, in addition, is fabricated from a metal woven fabric and/or a metal felt.
  • the closed structure of the inner wall makes it possible to minimize flow losses.
  • the inner wall made of the metal felt and/or of the metal woven fabric serves as a run-in lining.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US11/578,862 2004-03-03 2005-02-28 Ring structure of metal construction having a run-in lining Expired - Fee Related US8061965B2 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE102004010236A DE102004010236A1 (de) 2004-03-03 2004-03-03 Ringstruktur in Metallbauweise
DE102004010236 2004-03-03
DE102004010236.8 2004-03-03
PCT/DE2005/000333 WO2005085600A1 (de) 2004-03-03 2005-02-28 Ringstruktur in metallbauweise mit einlaufbelag

Publications (2)

Publication Number Publication Date
US20090263239A1 US20090263239A1 (en) 2009-10-22
US8061965B2 true US8061965B2 (en) 2011-11-22

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US11/578,862 Expired - Fee Related US8061965B2 (en) 2004-03-03 2005-02-28 Ring structure of metal construction having a run-in lining

Country Status (4)

Country Link
US (1) US8061965B2 (de)
EP (1) EP1721064B1 (de)
DE (2) DE102004010236A1 (de)
WO (1) WO2005085600A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9963993B2 (en) 2012-10-30 2018-05-08 MTU Aero Engines AG Turbine ring and turbomachine
US10472980B2 (en) * 2017-02-14 2019-11-12 General Electric Company Gas turbine seals
US11125101B2 (en) 2017-07-04 2021-09-21 MTU Aero Engines AG Turbomachine sealing ring

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2495399B1 (de) 2011-03-03 2016-11-23 Safran Aero Booster S.A. Segmentierter Stator-Außenring zum Kompensieren von Rotorverschiebungen gegenüber dem Stator
TR201705399A2 (tr) * 2017-04-11 2017-09-21 Sdm Siradisi Arge Ve Muehendislik Sanayi Ticaret Anonim Sirketi Örgü kumaş destekli yaprak keçe

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US3042365A (en) * 1957-11-08 1962-07-03 Gen Motors Corp Blade shrouding
US3053694A (en) * 1961-02-20 1962-09-11 Gen Electric Abradable material
US3056583A (en) * 1960-11-10 1962-10-02 Gen Electric Retaining means for turbine shrouds and nozzle diaphragms of turbine engines
US3068016A (en) * 1958-03-31 1962-12-11 Gen Motors Corp High temperature seal
US3126149A (en) * 1964-03-24 Foamed aluminum honeycomb motor
US3146992A (en) * 1962-12-10 1964-09-01 Gen Electric Turbine shroud support structure
US3365172A (en) * 1966-11-02 1968-01-23 Gen Electric Air cooled shroud seal
US3423070A (en) * 1966-11-23 1969-01-21 Gen Electric Sealing means for turbomachinery
US3425665A (en) * 1966-02-24 1969-02-04 Curtiss Wright Corp Gas turbine rotor blade shroud
US3583824A (en) * 1969-10-02 1971-06-08 Gen Electric Temperature controlled shroud and shroud support
US3867061A (en) 1973-12-26 1975-02-18 Curtiss Wright Corp Shroud structure for turbine rotor blades and the like
US4135851A (en) 1977-05-27 1979-01-23 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Composite seal for turbomachinery
US4409054A (en) * 1981-01-14 1983-10-11 United Technologies Corporation Method for applying abradable material to a honeycomb structure and the product thereof
US4529355A (en) * 1982-04-01 1985-07-16 Rolls-Royce Limited Compressor shrouds and shroud assemblies
US4666371A (en) * 1981-03-25 1987-05-19 Rolls-Royce Plc Gas turbine engine having improved resistance to foreign object ingestion damage
US4867639A (en) * 1987-09-22 1989-09-19 Allied-Signal Inc. Abradable shroud coating
US5228195A (en) * 1990-09-25 1993-07-20 United Technologies Corporation Apparatus and method for a stator assembly of a rotary machine
US5281089A (en) * 1990-09-25 1994-01-25 United Technologies Corporation Apparatus and method for a stator assembly of a rotary machine
US5304031A (en) * 1993-02-25 1994-04-19 The United States Of America As Represented By The Secretary Of The Air Force Outer air seal for a gas turbine engine
US5988975A (en) * 1996-05-20 1999-11-23 Pratt & Whitney Canada Inc. Gas turbine engine shroud seals
DE19828065A1 (de) 1998-06-24 1999-12-30 Bmw Rolls Royce Gmbh Wabenstruktur-Dichtung insbesondere für eine Gasturbine
DE10020673A1 (de) 2000-04-27 2001-10-31 Mtu Aero Engines Gmbh Gehäusestruktur in Metallbauweise
US6468026B1 (en) * 1998-11-13 2002-10-22 General Electric Company Blade containing turbine shroud
US6499943B1 (en) * 1999-08-09 2002-12-31 Alstom (Switzerland Ltd Friction-susceptible component of a thermal turbo machine
US6619913B2 (en) * 2002-02-15 2003-09-16 General Electric Company Fan casing acoustic treatment
US20040151582A1 (en) * 2002-08-03 2004-08-05 Faulkner Andrew Rowell Sealing of turbomachinery casing segments
US6962482B2 (en) * 2003-07-04 2005-11-08 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment

Patent Citations (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3126149A (en) * 1964-03-24 Foamed aluminum honeycomb motor
US3042365A (en) * 1957-11-08 1962-07-03 Gen Motors Corp Blade shrouding
US3068016A (en) * 1958-03-31 1962-12-11 Gen Motors Corp High temperature seal
US3056583A (en) * 1960-11-10 1962-10-02 Gen Electric Retaining means for turbine shrouds and nozzle diaphragms of turbine engines
US3053694A (en) * 1961-02-20 1962-09-11 Gen Electric Abradable material
US3146992A (en) * 1962-12-10 1964-09-01 Gen Electric Turbine shroud support structure
US3425665A (en) * 1966-02-24 1969-02-04 Curtiss Wright Corp Gas turbine rotor blade shroud
US3365172A (en) * 1966-11-02 1968-01-23 Gen Electric Air cooled shroud seal
US3423070A (en) * 1966-11-23 1969-01-21 Gen Electric Sealing means for turbomachinery
DE1551183A1 (de) 1966-11-23 1970-04-16 Gen Electric Zusammengesetzter Dichtungsbauteil fuer ein Turbinentriebwerk
US3583824A (en) * 1969-10-02 1971-06-08 Gen Electric Temperature controlled shroud and shroud support
US3867061A (en) 1973-12-26 1975-02-18 Curtiss Wright Corp Shroud structure for turbine rotor blades and the like
US4135851A (en) 1977-05-27 1979-01-23 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Composite seal for turbomachinery
US4409054A (en) * 1981-01-14 1983-10-11 United Technologies Corporation Method for applying abradable material to a honeycomb structure and the product thereof
US4666371A (en) * 1981-03-25 1987-05-19 Rolls-Royce Plc Gas turbine engine having improved resistance to foreign object ingestion damage
US4529355A (en) * 1982-04-01 1985-07-16 Rolls-Royce Limited Compressor shrouds and shroud assemblies
US4867639A (en) * 1987-09-22 1989-09-19 Allied-Signal Inc. Abradable shroud coating
US5228195A (en) * 1990-09-25 1993-07-20 United Technologies Corporation Apparatus and method for a stator assembly of a rotary machine
US5281089A (en) * 1990-09-25 1994-01-25 United Technologies Corporation Apparatus and method for a stator assembly of a rotary machine
US5304031A (en) * 1993-02-25 1994-04-19 The United States Of America As Represented By The Secretary Of The Air Force Outer air seal for a gas turbine engine
US5988975A (en) * 1996-05-20 1999-11-23 Pratt & Whitney Canada Inc. Gas turbine engine shroud seals
US6251494B1 (en) * 1998-06-24 2001-06-26 Rolls-Royce Deutschland Ltd & Co Kg Honeycomb structure seal for a gas turbine and method of making same
DE19828065A1 (de) 1998-06-24 1999-12-30 Bmw Rolls Royce Gmbh Wabenstruktur-Dichtung insbesondere für eine Gasturbine
US6468026B1 (en) * 1998-11-13 2002-10-22 General Electric Company Blade containing turbine shroud
US6499943B1 (en) * 1999-08-09 2002-12-31 Alstom (Switzerland Ltd Friction-susceptible component of a thermal turbo machine
DE10020673A1 (de) 2000-04-27 2001-10-31 Mtu Aero Engines Gmbh Gehäusestruktur in Metallbauweise
US6537020B2 (en) * 2000-04-27 2003-03-25 Mtu Aero Engines Gmbh Casing structure of metal construction
US6619913B2 (en) * 2002-02-15 2003-09-16 General Electric Company Fan casing acoustic treatment
US20040151582A1 (en) * 2002-08-03 2004-08-05 Faulkner Andrew Rowell Sealing of turbomachinery casing segments
US6962482B2 (en) * 2003-07-04 2005-11-08 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment

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* Cited by examiner, † Cited by third party
Title
Serope Kalpakjian and Steven R. Schmid, Manufacturing Processes for Engineering Materials, 2003, Prentice Hall, 4th Edition, pp. 689, 730. *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9963993B2 (en) 2012-10-30 2018-05-08 MTU Aero Engines AG Turbine ring and turbomachine
US10472980B2 (en) * 2017-02-14 2019-11-12 General Electric Company Gas turbine seals
US11125101B2 (en) 2017-07-04 2021-09-21 MTU Aero Engines AG Turbomachine sealing ring

Also Published As

Publication number Publication date
DE102004010236A1 (de) 2005-09-15
DE502005009677D1 (de) 2010-07-15
EP1721064A1 (de) 2006-11-15
WO2005085600A1 (de) 2005-09-15
EP1721064B1 (de) 2010-06-02
US20090263239A1 (en) 2009-10-22

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Owner name: MTU AERO ENGINES GMBH, GERMANY

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